Fundamental gear system architecture
원문보기
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0557614
(2012-07-25)
|
등록번호 |
US-8572943
(2013-11-05)
|
발명자
/ 주소 |
|
출원인 / 주소 |
- United Technologies Corporation
|
대리인 / 주소 |
Carlson, Gaskey & Olds, P.C.
|
인용정보 |
피인용 횟수 :
8 인용 특허 :
10 |
초록
▼
A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system a
A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing thermal energy equal to less than about 2% of power input into the gear system.
대표청구항
▼
1. A fan drive gear system for a gas turbine engine comprising: a gear system configured to provide a speed reduction between a fan drive turbine and a fan;a mount flexibly supporting portions of the gear system radially extending from a static structure of the gas turbine engine with respect to a c
1. A fan drive gear system for a gas turbine engine comprising: a gear system configured to provide a speed reduction between a fan drive turbine and a fan;a mount flexibly supporting portions of the gear system radially extending from a static structure of the gas turbine engine with respect to a central axis to accommodate radial movement between the gear system and the static structure; anda lubrication system configured to provide lubricant to the gear system and remove thermal energy produced by the gear system, wherein the lubrication system includes a maximum capacity for removing thermal energy from the gear system greater than zero and less than about 2% of power input into the gear system during operation of the engine. 2. The fan drive gear system as recited in claim 1, wherein the gear system is configured to transfer power input from the fan drive turbine to the fan at an efficiency greater than about 98% to less 100%. 3. The fan drive gear system as recited in claim 1, wherein the lubrication system includes a capacity for removing thermal energy equal to less than about 1% of power input into the gear system. 4. The fan drive gear system as recited in claim 1, wherein the lubrication system comprises a main lubrication system configured to provide lubricant flow to the gear system and an auxiliary lubrication system configured to provide lubricant to the gear system responsive to an interruption of lubricant flow from the main lubrication system. 5. The fan drive gear system as recited in claim 1, wherein the mount includes a load limiter for limiting movement of the gear system responsive to an unbalanced condition. 6. The fan drive gear system as recited in claim 1, wherein the gear system comprises a sun gear driven by the fan drive turbine, a non-rotatable carrier, a plurality of star gears supported on the carrier and driven by the sun gear and a ring gear circumscribing the plurality of star gears. 7. The fan drive gear system as recited in claim 6, wherein the mount includes a first flexible coupling between an input shaft driven by the fan drive turbine and the sun gear, and a second flexible coupling between a fixed structure and the carrier. 8. The fan drive gear system as recited in claim 1, wherein the gear system comprises a sun gear driven by the fan drive turbine, a rotatable carrier, a plurality of planet gears supported on the carrier and driven by the sun gear, and a ring gear circumscribing the plurality of planet gears. 9. The fan drive gear system as recited in claim 8, wherein the mount includes a first flexible coupling between an input shaft driven by the fan drive turbine and the sun gear, and a second flexible coupling between a fixed structure and the ring gear. 10. A gas turbine engine comprising: a fan including a plurality of fan blades rotatable about an axis;a compressor section;a combustor in fluid communication with the compressor section;a fan drive turbine in communication with the combustor;a gear system is configured to: (a) provide a speed reduction between the fan drive turbine and the fan; and (b), transfer power input from the fan drive turbine to the fan at an efficiency greater than about 98% to less 100%;a mount flexibly supporting the gear system radially extending from a static structure of the engine with respect to a central axis to accommodate radial movement between the gear system and the static structure; anda lubrication system configured to provide lubricant to the gear system and remove removing thermal energy from the gear system produced by the gear system. 11. The gas turbine engine as recited in claim 10, wherein the lubrication system includes a maximum capacity for removing thermal energy generated by the gear system greater than zero and less than about 2% of power input into the gear system during operation of the engine. 12. The gas turbine engine as recited in claim 10, wherein the lubrication system includes a capacity for removing thermal energy greater than zero to less than about 1% of power input into the gear system. 13. The gas turbine engine as recited in claim 10, wherein the lubrication system comprises a main lubrication system configured to provide lubricant flow to the gear system and an auxiliary lubrication system configured to provide lubricant to the gear system responsive to an interruption of lubricant flow from the main lubrication system. 14. The gas turbine engine as recited in claim 10, wherein the gear system comprises a sun gear driven by the fan drive turbine, a non-rotatable carrier, a plurality of star gears supported on the carrier and driven by the sun gear and a ring gear circumscribing the plurality of star gears and the mount includes a first flexible coupling between an input shaft driven by the fan drive turbine and the sun gear, and a second flexible coupling between a fixed structure and the carrier. 15. The gas turbine engine as recited in claim 10, wherein the gear system comprises a sun gear driven by the fan drive turbine, a rotatable carrier, a plurality of planet gears supported on the carrier and driven by the sun gear, and a ring gear circumscribing the plurality of planet gears and the mount includes a first flexible coupling between an input shaft driven by the fan drive turbine and the sun gear, and a second flexible coupling between a fixed structure and the ring gear. 16. The gas turbine engine as recited in claim 10, wherein the mount includes a load limiter for limiting movement of the gear system responsive to an unbalanced condition. 17. The gas turbine engine as recited in claim 10, wherein the gear system comprises a gear reduction having a gear ratio greater than about 2.3. 18. The gas turbine engine as recited in claim 10, wherein said fan delivers a portion of air into a bypass duct, and a bypass ratio being defined as the portion of air delivered into the bypass duct divided by the amount of air delivered into the compressor section, with the bypass ratio being greater than about 6.0. 19. The gas turbine engine as recited in claim 10, wherein a fan pressure ratio across the fan is less than about 1.5. 20. The gas turbine engine as recited in claim 10, wherein said fan has 26 or fewer blades.
이 특허에 인용된 특허 (10)
-
Sheridan William G. (Southington CT) Pagluica Gino J. (Manchester CT), Coupling system for a planetary gear train.
-
Sheridan, William G.; McCune, Michael E., Epicyclic gear system with improved lubrication system.
-
McCune, Michael E.; Husband, Jason, Flexible support structure for a geared architecture gas turbine engine.
-
Coffinberry George A. (Cincinnati OH) Kast Howard B. (Fairfield OH), Oil cooling system for a gas turbine engine.
-
Hadaway Edward S. (Derby GB2) Wedlake Norman J. (Bristol GB2), Reduction gear assembly and a gas turbine engine.
-
Treby John M. (Bristol GB2) Roberts Derek A. (Bristol GB2), Rotor drive systems.
-
Van Duyn Keven G. ; Pero Edward B., Rotor support for a turbine engine.
-
Sheridan William G. ; Shaffer Harold K., Seal assembly for an intershaft seal in a gas turbine engine.
-
Sheridan William G., Star gear system with lubrication circuit and lubrication method therefor.
-
McCune, Michael E.; Merry, Brian D.; Suciu, Gabriel L., Systems and methods involving multiple torque paths for gas turbine engines.
이 특허를 인용한 특허 (8)
-
Sheridan, William G., Fundamental gear system architecture.
-
Sheridan, William G., Gear system architecture for gas turbine engine.
-
Sheridan, William G.; McCune, Michael E., Geared gas turbine engine with reduced oil tank size.
-
Sheridan, William G., Geared turbofan with independent flexible ring gears and oil collectors.
-
Ketchum, David A.; Thoresen, James T.; James, Denman H.; James, Reade W.; Sheridan, William G., Lubricating a rotating component during forward and/or reverse rotation.
-
Niergarth, Daniel Alan; Prentice, Ian Francis; Kroger, Christopher James, Variable pitch fan blade retention system.
-
Miller, Brandon Wayne; Prentice, Ian Francis; Niergarth, Daniel Alan, Variable pitch fan for gas turbine engine and method of assembling the same.
-
Niergarth, Daniel Alan; Miller, Brandon Wayne; Bradley, Donald Albert, Variable-pitch rotor with remote counterweights.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.